Abstract: A device of an aircraft engine for separating oil from an air-oil volume flow and an apparatus for introducing oil into the air-oil volume flow. An outlet area of the apparatus for introducing oil is provided in a closed line section, into which the air-oil volume flow can be introduced via an inlet area. In accordance with the invention, a flow cross-section of the line section downstream of the outlet area of the apparatus tapers at least partially like a nozzle and at least in some sections inside a confusor area.

Abstract: An electronically controlled suspension system for a bicycle includes at least one spring element between first and second parts the bicycle, both parts being movably interconnected. At least one parameter of the spring element is modified. At least one actuator influences the spring element to modify the at least one parameter. An electronic module produces a control signal for the at least one actuator. A control device is influenced by the control signal produced by the electronic module. The control device is connected to at least one of the electronic module and the actuator through a radio signal. A corresponding method controls the suspension system for the bicycle and a computer program executes the method.

Abstract: The present invention describes a device of a jet engine with at least one component arranged in a casing and designed rotatable relative to said casing. At least one air-oil volume flow can be passed out of an area of the jet engine into the casing. In accordance with the invention the air-oil volume flow can be introduced into the casing via an introducing facility at least approximately tangentially to an area of the rotatable component close to at least an outer circumferential area.

Abstract: The present invention describes a jet engine with a device for spraying oil into an air-oil volume flow guided inside a flow cross-section limited by a wall area. The air-oil volume flow is guidable through an oil separator in order to separate the oil. In accordance with the invention, the oil can be sprayed into the air-oil volume flow in the area of the device via an outlet area rigidly connected to the wall area.

Abstract: The present invention describes a jet engine with a device for spraying oil into an air-oil volume flow guided inside a flow cross-section limited by a wall area. The air-oil volume flow is guidable through an oil separator in order to separate the oil. In accordance with the invention, the oil can be sprayed into the air-oil volume flow in the area of the device via an outlet area designed movable relative to the wall area.

Abstract: An accessory gearbox for an engine having at least one accessory gearbox shaft connectable to an auxiliary unit and driveable by a drive shaft, the drive shaft being operatively connectable to an engine shaft of the engine. At least one auxiliary unit can be arranged on the drive shaft and/or in the area of the operative connection between the drive shaft and the engine shaft and/or on an accessory gearbox shaft connectable to a further auxiliary unit.

Abstract: The present invention proposes a generator for arrangement on a shaft of an accessory gearbox of an engine with a stator and with a rotor which can be coupled to a shaft of the accessory gearbox of the engine and which is rotatably mounted relative to the stator, where a stator area receiving the stator can be separated from a rotor area receiving the rotor. The rotor can be supplied with cooling medium in the rotor area. It furthermore proposes an accessory gearbox of an engine with a drive shaft operatively connectable to a main shaft of the engine and with at least one generator arranged on a shaft of the accessory gearbox.

Abstract: The present invention proposes an accessory gearbox for an engine with a drive shaft operatively connectable to a main shaft of the engine, with an extension shaft being provided which can be put into a detachable operative connection to the drive shaft substantially coaxially to said drive shaft of the accessory gearbox At least one auxiliary unit can be detachably arranged on the extension shaft.

Abstract: The present invention describes a jet engine with at least one oil separator, through which an air-oil volume flow can be guided out of at least one area supplied with oil for separating the oil. In accordance with the invention the air-oil volume flow from the area supplied with oil can be introduced into the oil separator via an interior of an accessory gearbox casing. The air can be discharged from the oil separator via an air outlet and the oil via an oil outlet.

Abstract: A jet engine includes at least one oil separator, through which an air-oil volume flow can be guided out of several areas supplied with oil for separating the oil, where a device for spraying oil into the air-oil volume flow is provided. Oil can be sprayed in using the device in the area of each connection between an area supplied with oil and the oil separator and/or downstream of a combining area between at least two air-oil volume flows from two or more areas supplied with oil.

Abstract: A gas turbine engine assembly is connected to a pylon for mounting the gas turbine engine to an aircraft. The assembly has a frame supporting at least one accessory independently of the gas turbine engine. Frame is attached to the pylon at forward and rearward engine mounting locations. The frame includes at least one hollow tube and at least one hollow tube is fluid tight. The one hollow tube is evacuated or contains pressurised fluid and a pressure sensor is provided to detect a change in pressure in the at least one hollow tube to determine if there is a leak in the at least one hollow tube and hence if the frame is damaged. This ensures that the frame may be repaired or replaced before there is a loss of operation of one or more of the accessories which may result in a failure of the gas turbine engine.

Abstract: A gas turbine engine assembly is connected to a pylon for mounting the gas turbine engine to an aircraft. The assembly has a frame supporting at least one accessory independently of the gas turbine engine. The frame is attached to the pylon at forward and rearward engine mounting locations. The frame comprises at least one hollow tube and at least one duct is arranged to supply coolant into the at least one hollow tube and the at least one hollow tube is arranged to supply coolant to the at least one accessory.

Abstract: The invention relates to a suspension fork (1) having at least one positive chamber (31), at least one negative chamber (32) and an adjusting device (40) for adjusting the length of the suspension fork (1), the adjusting device (40) comprising a valve means (50) which is arranged between the at least one positive chamber (31) and the at least one negative chamber (32), and an actuation device (60), characterized in that the actuation device (60) has at least one first position for adjusting a short length of the suspension fork (1) (lowered suspension fork) and at least one second position for adjusting a long length of the suspension fork (1) (extended suspension fork).

Abstract: The present invention proposes an accessory gearbox for an engine having at least one accessory gearbox shaft connectable to an auxiliary unit and driveable by a drive shaft, said drive shaft being operatively connectable to an engine shaft of the engine. At least one auxiliary unit can be arranged on the drive shaft and/or in the area of the operative connection between the drive shaft and the engine shaft and/or on an accessory gearbox shaft connectable to a further auxiliary unit.

Abstract: The present invention proposes a structural unit for an aircraft engine having at least one fuel pump of a fuel circuit and at least one hydraulic fluid pump of a hydraulic fluid circuit, where the structural unit can be coupled to an accessory gearbox shaft of an accessory gearbox of the engine.

Abstract: The present invention proposes an accessory gearbox (9) for an engine with a drive shaft (12) operatively connectable to a main shaft of the engine, with an extension shaft (29) being provided which can be put into a detachable operative connection to the drive shaft (12) substantially coaxially to said drive shaft (12) of the accessory gearbox (9). At least one auxiliary unit (39) can be detachably arranged on the extension shaft (29).

Abstract: The present invention proposes a generator for arrangement on a shaft of an accessory gearbox of an engine with a stator and with a rotor which can be coupled to a shaft of the accessory gearbox of the engine and which is rotatably mounted relative to the stator, where a stator area receiving the stator can be separated from a rotor area receiving the rotor. The rotor can be supplied with cooling medium in the rotor area. It furthermore proposes an accessory gearbox of an engine with a drive shaft operatively connectable to a main shaft of the engine and with at least one generator arranged on a shaft of the accessory gearbox.